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Unformatted text preview: a) For a turbojet engine with a compressor pressure ratio of 25, and a turbine inlet temperature of 1800K, under what flight conditions (Mach number) would the compressor inlet temperature limit be exceeded? Consider performance at sea-level (Tatm=300K) and at 10km (Tatm = 216K) b) At a constant flight Mach number of 1.2, how much do the thermal and propulsive efficiency change between altitudes of sea-level and 10km? Explain this behavior. c) If you were forced to reduce the turbine inlet temperature to 1400K because the turbine durability Copyright Rolls-Royce plc. Reproduced with the kind permission of Rolls-Royce plc. group was having difficulty designing the blades to withstand temperatures of 1800K, how would it impact the performance of the vehicle (consider M=1.2 and 10km only)?...
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- Fall '05
- Propulsion, Gas compressor, turbine inlet temperature